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    Film-Cooling on a Gas Turbine Blade Pressure Side or Suction Side With Compound Angle Shaped Holes 

    Source: Journal of Turbomachinery:;2009:;volume( 131 ):;issue: 001:;page 11019
    Author(s): Zhihong Gao; Diganta P. Narzary; Je-Chin Han
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: The film-cooling effectiveness on the surface of a high pressure turbine blade is measured using the pressure sensitive paint technique. Compound angle laidback fan-shaped holes are used to cool ...
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    Influence of Coolant Density on Turbine Blade Platform Film-Cooling 

    Source: Journal of Thermal Science and Engineering Applications:;2012:;volume( 004 ):;issue: 002:;page 21002
    Author(s): Diganta P. Narzary; Kuo-Chun Liu; Je-Chin Han
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Detailed parametric study of film-cooling effectiveness was carried out on a turbine blade platform of a five-blade linear cascade. The parameters chosen were freestream turbulence intensity, ...
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    Influence of Coolant Density on Turbine Blade Film-Cooling Using Pressure Sensitive Paint Technique 

    Source: Journal of Turbomachinery:;2012:;volume( 134 ):;issue: 003:;page 31006
    Author(s): Diganta P. Narzary; Kuo-Chun Liu; Akhilesh P. Rallabandi; Je-Chin Han
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Adiabatic film-cooling effectiveness is examined on a high-pressure turbine blade by varying three critical engine parameters, viz., coolant blowing ratio, coolant-to-mainstream density ratio, and ...
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